Hybrid part made from monolithic ceramic skin and CMC core

ABSTRACT

A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material. A ceramic matrix composite material is located adjacent interior portions of the platform and the attachment feature and is bonded to the monolithic ceramic material.

BACKGROUND

The present disclosure is directed to a hybrid part, such as a turbineblade or vane, which is made from a monolithic ceramic skin and aceramic matrix composite (CMC) core.

Currently, parts, such as turbine blades and vanes, for use in turbineengine components are made from metallic materials. Such parts areexposed to high temperatures during their service life. To increasetheir life, it is necessary to provide the parts with internal coolingcircuits which may cause a decrease in engine efficiency.

Interest has been expressed in the development of parts using ceramicmaterials. This is because parts formed from ceramic materials canwithstand high temperatures without any need for internal cooling.

SUMMARY

In accordance with the present disclosure, there is provided a hybridpart broadly comprising an attachment feature, an exterior portion ofsaid attachment feature being formed from a monolithic ceramic material,and a ceramic matrix composite material located adjacent interiorportions and said attachment feature and being bonded to said monolithicceramic material.

Further, in accordance with the present disclosure, there is provided amethod for forming a hybrid part. The method broadly comprises the stepsof: casting or shaping a shell having an attachment feature with a corepassage located internally of said attachment feature, said casting stepcomprising forming or shaping said shell from a monolithic ceramicmaterial powder, densifying said shell, drawing a ceramic matrixcomposite material preform through the core passage, and bonding theceramic composite material preform to an interior wall of the monolithicceramic material forming the shell.

Other details of the hybrid part made from monolithic ceramic skin and aceramic matrix composite core are set forth in the following detaileddescription and the accompanying drawings wherein like referencenumerals depict like elements.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is an end view of a part in accordance with the presentdisclosure;

FIG. 2 is a side view of the part of FIG. 1;

FIG. 3 is a sectional view taken along lines 3-3 in FIG. 2;

FIG. 4 is a sectional view taken along lines 4-4 in FIG. 2;

FIG. 5 is a sectional view taken along lines 5-5 in FIG. 2;

FIG. 6 is a sectional view taken along lines 6-6 in FIG. 2; and

FIG. 7 is a flowchart of a method for forming the part of FIG. 1.

DETAILED DESCRIPTION

Referring now to the drawings, there is shown in FIGS. 1 and 2 a hybridpart 10 for use in a gas turbine engine. The hybrid part 10 may be ablade or a vane. The hybrid part 10 includes an attachment featureportion 14, such as a dovetail portion and a platform 18. The attachmentfeature portion 14 and the platform 18 each comprise a shell 20 formedfrom a cast monolithic ceramic material. Suitable materials which may beused to form the shell 20 include, but are not limited to, siliconnitride and/or silicon carbide.

As can be seen from FIG. 3, a core passage 22 is located within theshell 20 forming the attachment feature portion 14 and the platform 18.As shown in FIGS. 3-6, the core passage 22 extends continuously from abase end 21 of the hybrid part to a region adjacent a tip portion 26 ofthe hybrid part 10. As shown in FIG. 4, the core passage 22 has a firstchordwise dimension D1 in the attachment feature portion region. As canbe seen from FIG. 6, the core passage 22 has a second chordwisedimension D2 in the region adjacent the tip portion 26, which secondchordwise dimension D2 is smaller than the first chordwise dimension D1.Thus, the core passage 22 tapers from a region 27 in proximity to theplatform 18 to the region adjacent the tip portion 26.

Located within the central core passage 22 is a ceramic matrix compositematerial 23. The ceramic matrix composite material may comprise aplurality of fibers 24. The fibers 24 may be formed from a collection ofindividual fibers such as silicon carbide, carbon, and/or a monofilamentfiber. The monofilament fiber consists of a central carbon fiber coreand a silicon carbide outer layer. The fibers 24 may be laid in anyspanwise direction, but typically they are primarily configured as 0°fibers. The fibers 24, after densification and pyrolysis with a siliconcarbide ceramic matrix or a glass matrix, form an internal spar which isbonded to an interior surface 19 of the shell 20 and which helpsstrengthen the part.

The densification process can consist of several types of processes orcombination of different processes to achieve a final ceramic matrixwith 0-5% residual porosity, and preferably 0-2% residual porosity. Thedensification processes can be Polymer pre-impregnation, polymerinfiltration and pyrolosis (PIP), chemical vapor infiltration (CVI),chemical vapor deposition (CVD), glass injection, glass infiltration,metal melt infiltration or metal reaction infiltration.

Polymer pre-impregnation and PIP both use a form of polymer resin thatwill decompose into ceramic material upon exposure to high temperatures.For pre-impregnation, the resin is applied to the fibers beforeinsertion into the core, and for PIP the polymer is added after they areinstalled into the core. Due to the chemical conversion of the polymerduring heating, some reduction in volume of the resulting ceramic matrixoccurs and results in cracking and porosity. Multiple PIP cycles may beused after the first pre-impregnation or PIP cycle to fill the voids andreduce the porosity.

Chemical vapor infiltration and chemical vapor deposition are similarprocesses where the ceramic matrix constituents are transported to thefibers by a vapor cloud. Build up of the ceramic matrix occur as layerupon layer of molecules are added to the existing fibers and matrix. Insome cases individual atomic species are deposited, but more often twoor more atomic species in vapor react and deposit out onto the fibers.CVI/CVD can be used before and/or after pre-impregnation or PIP cyclesto reduce porosity.

Glass infiltration and glass injection involve adding a glass matrixinto the fibers. In the glass infiltration the glass may be added to thefibers in a powder form then allowed to melt into the fibers under heat.In glass injection, hot glass matrix flows or is forced into the fibers.In both cases, after the temperature is reduced the glass solidifies andforms the glass/fiber structure. Final processing may includecrystallization of the glass matrix.

Metal melt infiltration and metal reaction infiltration involve theaddition of a metal, typically silicon, into an existing ceramic matrixto fill the residual porosity that may be present after the polymerpre-impregnation, PIP, CVI or CVD processes. In the metal meltinfiltration process liquid silicon or other metals fills the openporosity in the fiber preform. In the metal reaction infiltration,liquid metal chemically reacts with excess elements within the ceramicmatrix to form additional ceramic matrix material. Typically liquidsilicon reacts with excess carbon to form silicon carbide.

Referring now to FIG. 4, there is shown a sectional view of theattachment feature portion 14 of the hybrid part 10. As can be seen fromthis figure, the hybrid part 10 in this region has the monolithicceramic material shell 20 with the central core passage 22 and thefibers 24 forming the ceramic matrix composite material positionedwithin the central core passage 22.

Referring now to FIG. 5, there is shown a sectional view of an airfoilportion 16 of the part taken at the approximate mid-span of the airfoilportion. As before, the hybrid part 10 is characterized by a monolithicceramic material shell 20 with a central core passage 22 and the ceramicmatrix composite material fibers 24 positioned within the central corepassage 22.

Referring now to FIG. 6, there is shown a sectional view of the airfoilportion 16 in a region proximate to the airfoil tip portion 26. As shownin the figure, the part 10 has a ceramic shell 20 with a smaller centralcore passage 22 in the vicinity of the leading edge 34 of the part 10and the fibers 24 positioned within the central core passage 22. As aresult of the tapering of the core passage 22, the airfoil portion 16 ofthe blade is primarily formed from the ceramic matrix composite materialwhich comprises fibers 28 of the ceramic matrix composite materialembedded within the shell 20.

The design of the hybrid part 10 has merit because it is a simplerdesign as compared to a complete ceramic matrix composite blade,platform and attachment feature.

Referring now to FIG. 7, the part 10 may be formed in step 100 by firstcasting or shaping the shell 20 from a monolithic ceramic material inpowder form. The ceramic material may be placed into a mold so that theshell 20 is formed with the attachment feature and the platform.Additional features such as damper pockets may be provided if desired.The shell 20 is formed with the core passage 22 having openings at eachend.

The ceramic material within the mold may be fully densified in step 102using any technique known in the art, which include, but are not limitedto, sintering, gas pressure sintering, reaction sintering, reactionbonding hot isostatic pressing, hot pressing, and infiltrationtechniques. The resulting shell 20 is formed from an isotropic material.

After densification, in step 104, the fibers 24 formed from a ceramicmatrix composite material preform, with a polymer precursor applied tothe fibers 24, may be drawn into the open core passage 22. Prior toinsertion, the fibers 24 may be formed into an core preform shape usinga low temperature molding process such as, but not limited to,autoclave, compression molding, or resin transfer molding.

In step 106, the ceramic matrix composite material preform with thefibers 24 and the shell 20 may be subjected to a pyrolysis technique todensify the matrix and bond the ceramic matrix composite material withthe fibers 24 to the shell 20. The polymer precursor applied to thefibers partially infiltrates the monolithic ceramic forming the shell 20during the pyrolysis. A strong bond is formed between the monolithicceramic material forming the shell 20 and the fibers 24 forming thespar.

In lieu of a pyrolysis technique, the fibers 24 may be subjected to achemical vapor deposited matrix. For example, a silicon carbide ceramicmatrix may be deposited on the fibers 24. Alternatively, a glassinjected or glass infiltrated matrix may be used for lower temperatureapplications and/or lower cost.

Following densification, in step 108, any fibers 24 protruding from thetip portion 26 of the hybrid part 10 or the attachment feature 14 of thehybrid part 10 may be ground away if needed.

A hybrid part formed in accordance with the instant disclosure may becharacterized by a high fracture toughness in the radial and bendingmodes, a simple load path in the ceramic matrix composite, and highlyrepeatable features. Since ceramic powders are substantially cheaper tomake than ceramic fibers, the reduction in the use of fibers would dropthe raw material cost considerably. Add in the reduction in ply layuptime, cutting fabric, weaving the fabric, the cost of manufacturing andrisk drop again. Further, it should be noted that monolithic ceramicsare five to ten times stronger than composite matrix materials.Therefore, the complex features on the part are quite strong. Thefeatures are less prone to fracture. The tough core formed by theceramic matrix composite material helps protect the part from fractureduring service events.

A blade or vane formed by method of the present disclosure may becharacterized by thin sections, such as thin leading and trailing edges.

While the part has been described in the context of a blade or vane usedin the gas turbine engine, other parts can be formed using the techniquedescribed herein. For example, the technique described herein may beused to form combustor liners, panels and/or bonded features.

There has been provided in accordance with the instant disclosure ahybrid part made from a monolithic ceramic skin and a ceramic matrixcomposite core. While the part of the present invention has beendescribed in the context of specific embodiments thereof, otherunforeseen alternatives, modifications, and variations may becomeapparent to those skilled in the art having read the foregoingdescription. Accordingly, it is intended to embrace those alternatives,modifications, and variations as fall within the broad scope of theappended claims.

What is claimed is:
 1. A hybrid part comprising: an attachment feature;an exterior portion of said attachment feature being formed from amonolithic ceramic material; and a ceramic matrix composite materiallocated adjacent interior portions of said attachment feature and beingbonded to said monolithic ceramic material wherein said interiorportions include a continuous core which extends from said attachmentfeature portion to a tip of said part, wherein said core is exposed atthe tip.
 2. The hybrid part of claim 1, wherein a portion of saidceramic matrix composite material is located within said continuouscore.
 3. The hybrid part of claim 2, wherein said continuous core has afirst chordwise dimension in said attachment feature and a secondchordwise dimension in a leading edge of said tip and said secondchordwise dimension is smaller than said first chordwise dimension. 4.The hybrid part of claim 1, wherein said ceramic matrix compositematerial extends in a spanwise direction from said attachment feature toa tip of said part and forms an airfoil portion.
 5. The hybrid part ofclaim 1, wherein said ceramic matrix composite material comprises aplurality of silicon carbide fibers.
 6. The hybrid part of claim 1,wherein said ceramic matrix composite material comprises a plurality ofcarbon fibers.
 7. The hybrid part of claim 1, wherein said ceramicmatrix composite material comprises a plurality of monofilament fibers.8. The hybrid part of claim 7, wherein each of said monofilament fiberscomprises a carbon fiber core and a silicon carbide coating.
 9. Thehybrid part of claim 1, wherein said ceramic matrix composite materialcomprises a matrix formed from one of silicon carbide and a glassmaterial.
 10. The hybrid part of claim 1, wherein said monolithicceramic material comprises at least one of silicon nitride and siliconcarbide.
 11. The hybrid part of claim 1 is a turbine blade or turbinevane.
 12. The hybrid part of claim 1, further comprising a platform.